Internal core profile for a turbine nozzle airfoil

ABSTRACT

First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.

The present invention relates to a nozzle airfoil of a stage of a gas turbine and particularly relates to a first stage turbine nozzle airfoil internal core profile.

Many system requirements must be met for each stage of the hot gas path section of a gas turbine in order to meet design goals. Particularly, the nozzle segments of the first stage of the turbine section must meet the operating requirements for that particular stage and also meet requirements for nozzle airfoil cooling flow efficiency, life and wall thickness distribution.

BACKGROUND OF THE INVENTION

In accordance with a preferred embodiment of the present invention, there is provided a unique internal core profile for a nozzle airfoil of a gas turbine, preferably the first stage nozzle, which enhances the performance of the gas turbine. It will be appreciated that the external shape of the nozzle airfoil improves its interaction with the buckets forming the stages of the turbine. Concomitantly the internal core profile shape of the nozzle airfoil is also significant for structural reasons as well as to optimize internal cooling with appropriate wall thickness. The nozzle airfoil internal core profile is defined by a unique loci of points which achieve the necessary structural and cooling requirements whereby improved turbine performance is obtained. This unique loci of points define the internal nominal core profile and are identified by the X, Y and Z Cartesian coordinates of Table I which follows. The 1,200 points for the coordinate values shown in Table I are for a cold, i.e., room temperature nozzle airfoil at various cross-sections of the nozzle airfoil along its length. The positive X, Y and Z directions are axial toward the exhaust end of the turbine, tangential in the direction of engine rotation looking aft and radially outwardly toward the outer platform, respectively. The X and Y coordinates are given in distance dimensions, e.g., units of inches, and are joined smoothly at each Z location to form a smooth continuous internal core profile cross-section. The Z coordinates are given in inches in distances along radii from the turbine axis. Each internal core profile section in the X, Y plane is joined smoothly with the adjacent profile sections in the Z direction to form, using the Table I coordinate values, the complete internal nozzle airfoil core profile.

Table I provides coordinate values for the complete internal core airfoil shape passing through the inner and outer platforms and the airfoil therebetween. The physical shape of the internal core profile between the inner and outer platforms is given in Table I by the airfoil sections defined between Z value limits of 22.200 and 25.050.

It will be appreciated that as each nozzle airfoil heats up in use, the internal core profile will change. Thus, the cold or room temperature profile is given by the X, Y and Z coordinates for manufacturing purposes. Because a manufactured internal nozzle airfoil core profile may be different from the nominal profile given by the following table, a distance of ±0.030 inches from the nominal profile in a direction normal to any surface location along the nominal profile defines a profile envelope for this internal nozzle airfoil core profile. The profile is robust to this variation without impairment of the mechanical cooling and aerodynamic functions of the airfoil.

In accordance with a preferred embodiment of the present invention, there is provided a turbine nozzle segment including inner and outer platforms and an airfoil extending between the platforms, the airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein the Z values between the limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between the limits being joined smoothly with one another to form the airfoil internal core profile.

In accordance with a further embodiment of the present invention, there is provided a turbine comprising a plurality of nozzle segments arranged in a circumferential array about an axis of the turbine, each nozzle segment including inner and outer platforms and at least one airfoil extending between the platforms, each airfoil having an internal nominal core profile at least least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between the limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between the Z value limits, the profile sections at the Z distances between the limits being joined smoothly with one another to form the airfoil internal core profile.

In accordance with a further embodiment of the present invention, there is provided a turbine nozzle segment including inner and outer platforms and an airfoil extending between the platforms, the airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil internal core profile.

In accordance with another embodiment of the present invention, there is provided a turbine comprising a plurality of nozzle segments in a circumferential array about an axis of the turbine, each segment having inner and outer platforms and at least one airfoil extending between the platforms, each airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from the turbine axis to planes extending normal to the radii, and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil internal core profile.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic representation of a hot gas path through multiple stages of a gas turbine and illustrates a first stage nozzle airfoil according to a preferred embodiment of the present invention;

FIG. 2 is a perspective view of a nozzle segment with an internal nozzle airfoil core profile depicted in full lines according to a preferred embodiment of the present invention with the nozzle airfoil shown in conjunction with inner and outer platforms and remaining portions of the nozzle airfoil illustrated by the dashed lines;

FIG. 3 is a circumferential perspective view of the nozzle airfoil internal core profile of FIG. 2 and associated airfoil and platforms;

FIG. 4 is a perspective view from above the outer platform of the internal core profile including the associated airfoil and platform; and

FIG. 5 is a cross-sectional view of the nozzle airfoil taken generally about on line 5-5 in FIG. 3.

DETAILED DESCRIPTION OF THE INVENTION

Referring now to the drawings, particularly to FIG. 1, there is illustrated a hot gas path, generally designated 10, of a gas turbine 12 including a plurality of turbine stages. Three stages are illustrated. For example, the first stage comprises a plurality of circumferentially spaced nozzles 14 and buckets 16. The nozzles 14 are circumferentially spaced one from the other and fixed about the axis of the rotor. First stage buckets 16 are mounted on the turbine rotor 17. A second stage of the turbine 12 is also illustrated, including a plurality of circumferentially spaced nozzles 18 and a plurality of circumferentially spaced buckets 20 mounted on the rotor 17. The third stage is also illustrated including a plurality of circumferentially spaced nozzles 22 and buckets 24 mounted on rotor 17. It will be appreciated that the nozzles and buckets lie in the hot gas path 10 of the turbine, the direction of flow of the hot gas through the hot gas path 10 being indicated by the arrow 26.

Referring now to FIG. 2, there is illustrated a nozzle segment generally designated 30 in which one or more airfoils 32 are disposed between inner and outer platforms 34 and 36, respectively. It will be appreciated that a plurality of nozzle segments 30 are disposed in a circumferential array about the turbine axis to form an annular flow path with the airfoils 32 guiding the hot gas to the follow-on buckets of the stage, e.g., the first stage buckets 16. The vanes 32 of the nozzle segments 30 are cooled by flowing air internally within the airfoils 32 and between the inner and outer platforms 34 and 36, respectively.

The internal core shape of the nozzle airfoil is indicated by the full lines 38 in the drawing figures. In FIG. 5, the internal core shape 38 is in the general form of an airfoil having internal wall surfaces 40 and 42 adjacent suction and pressure external surfaces of the airfoil, respectively, which, with the internal core profile 38, define an airfoil wall thickness t. The internal core profile extends through the inner and outer platforms 34 and 36.

To define the internal core shape of each nozzle airfoil including within the inner and outer platforms, there is provided a unique set of loci of points in space that meet the stage requirements, cooling areas, wall thickness, and can be manufactured. This unique loci of points which define the internal nozzle airfoil core profile 38 comprises a set of 1,200 points relative to the axis of rotation of the turbine. A Cartesian coordinate system of X, Y and Z values given in Table I below define this internal core profile 38 of the nozzle airfoil at various locations along its length. The coordinate values for the X and Y coordinates are set forth in inches in Table I although other units of dimensions may be used when the values are appropriately converted. The Z values set forth in Table I are radial distances from a turbine axis to planes extending normal to the radii. The Cartesian coordinate system has orthogonally related X, Y and Z axes and the X axis lies parallel to the turbine rotor center line, i.e., the rotary axis, and a positive X coordinate value is axial toward the aft, i.e., exhaust end of the turbine. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor, looking aft, and the positive Z coordinate value is radially outwardly toward the outer platform.

By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the internal core profile 38 of the nozzle airfoil representatively illustrated by the full lines in the drawing figures, at each Z distance along the length of the nozzle airfoil can be ascertained. By connecting the X and Y values with smooth continuing arcs, each internal core profile section 38 at each distance Z is fixed. The internal core profiles of the various internal locations between the distances Z are determined by smoothly connecting the adjacent profile sections 38 to one another to form the core profile. These values represent the internal core profiles at ambient non-operating or non-hot conditions.

The Table I values are generated and shown to three decimal places for determining the internal core profile of the nozzle airfoil. There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual internal profile of the nozzle airfoil. Accordingly, the values for the profile given in Table I are for a nominal internal nozzle airfoil core profile. It will therefore be appreciated that ± typical manufacturing tolerances, i.e., ± values, including any coating thicknesses, are additive to the X and Y values given in Table I below. Accordingly, a distance of ±0.030 inches in a direction normal to any surface location along the internal core profile defines an internal core profile envelope for this particular nozzle airfoil design and turbine, i.e., a range of variation between measured points on the actual internal core profile at nominal cold or room temperature and the ideal position of those points as given in Table I below at the same temperature. The internal core profile is robust to this range of variation without impairment of mechanical and cooling functions.

The Table I values below provide the X, Y, Z Cartesian values for the internal core of the airfoil including through the inner and outer platforms. The physical configuration of the internal core profile between the inner and outer platforms is provided by Table I between Z value limits of 22.200 and 25.050. These Z value limits commence radially outwardly of the inner platform and radially inwardly of the outer platform, respectively and define the physical shape of the internal core profile between those limits.

The coordinate values given in Table I below provide the preferred nominal internal core profile envelope through the nozzle airfoil including through the inner and outer platforms. X Y Z −0.582 −2.413 21.250 −0.587 −2.466 21.250 −0.591 −2.361 21.250 −0.604 −2.516 21.250 −0.611 −2.312 21.250 −0.632 −2.560 21.250 −0.641 −2.269 21.250 −0.662 −2.604 21.250 −0.679 −2.233 21.250 −0.692 −2.648 21.250 −0.721 −2.692 21.250 −0.724 −2.205 21.250 −0.750 −2.736 21.250 −0.773 −2.185 21.250 −0.779 −2.781 21.250 −0.807 −2.826 21.250 −0.825 −2.174 21.250 −0.834 −2.871 21.250 −0.862 −2.916 21.250 −0.877 −2.173 21.250 −0.889 −2.961 21.250 −0.916 −3.007 21.250 −0.930 −2.181 21.250 −0.943 −3.052 21.250 −0.970 −3.098 21.250 −0.980 −2.198 21.250 −0.997 −3.143 21.250 −1.023 −3.189 21.250 −1.028 −2.219 21.250 −1.050 −3.235 21.250 −1.076 −3.281 21.250 −1.077 −2.239 21.250 −1.101 −3.327 21.250 −1.126 −2.260 21.250 −1.127 −3.374 21.250 −1.152 −3.421 21.250 −1.174 −2.281 21.250 −1.177 −3.467 21.250 −1.202 −3.514 21.250 −1.222 −2.303 21.250 −1.227 −3.560 21.250 −1.252 −3.607 21.250 −1.270 −2.326 21.250 −1.278 −3.653 21.250 −1.303 −3.699 21.250 −1.318 −2.349 21.250 −1.329 −3.746 21.250 −1.406 −3.884 21.250 −1.412 −2.397 21.250 −1.433 −3.930 21.250 −1.458 −2.423 21.250 −1.459 −3.976 21.250 −1.486 −4.021 21.250 −1.504 −2.449 21.250 −1.514 −4.067 21.250 −1.542 −4.111 21.250 −1.549 −2.476 21.250 −1.571 −4.155 21.250 −1.594 −2.505 21.250 −1.602 −4.199 21.250 −1.634 −4.241 21.250 −1.638 −2.534 21.250 −1.669 −4.280 21.250 −1.681 −2.565 21.250 −1.708 −4.316 21.250 −1.723 −2.597 21.250 −1.752 −4.345 21.250 −1.764 −2.630 21.250 −1.801 −4.364 21.250 −1.804 −2.665 21.250 −1.843 −2.701 21.250 −1.853 −4.372 21.250 −1.880 −2.738 21.250 −1.906 −4.369 21.250 −1.917 −2.776 21.250 −1.953 −2.815 21.250 −1.958 −4.359 21.250 −1.989 −2.854 21.250 −2.008 −4.343 21.250 −2.024 −2.894 21.250 −2.058 −4.324 21.250 −2.059 −2.933 21.250 −2.093 −2.974 21.250 −2.106 −4.302 21.250 −2.127 −3.015 21.250 −2.154 −4.279 21.250 −2.160 −3.056 21.250 −2.193 −3.097 21.250 −2.201 −4.255 21.250 −2.226 −3.139 21.250 −2.248 −4.231 21.250 −2.258 −3.180 21.250 −2.290 −3.223 21.250 −2.295 −4.208 21.250 −2.385 −3.350 21.250 −2.391 −4.162 21.250 −2.417 −3.392 21.250 −2.435 −4.134 21.250 −2.448 −3.435 21.250 −2.475 −4.099 21.250 −2.479 −3.478 21.250 −2.510 −4.059 21.250 −2.510 −3.520 21.250 −2.539 −4.015 21.250 −2.540 −3.564 21.250 −2.562 −3.967 21.250 −2.567 −3.610 21.250 −2.581 −3.918 21.250 −2.588 −3.658 21.250 −2.588 −3.658 21.250 −2.595 −3.867 21.250 −2.602 −3.709 21.250 −2.604 −3.815 21.250 −2.607 −3.762 21.250 −0.555 −2.141 21.725 −0.564 −2.197 21.725 −0.565 −2.086 21.725 −0.585 −2.250 21.725 −0.594 −2.037 21.725 −0.607 −2.303 21.725 −0.628 −2.355 21.725 −0.637 −2.000 21.725 −0.649 −2.408 21.725 −0.671 −2.461 21.725 −0.688 −1.975 21.725 −0.692 −2.513 21.725 −0.714 −2.566 21.725 −0.735 −2.619 21.725 −0.744 −1.966 21.725 −0.757 −2.671 21.725 −0.778 −2.724 21.725 −0.800 −2.777 21.725 −0.800 −1.972 21.725 −0.821 −2.829 21.725 −0.842 −2.882 21.725 −0.853 −1.993 21.725 −0.864 −2.935 21.725 −0.885 −2.987 21.725 −0.897 −2.028 21.725 −0.907 −3.040 21.725 −0.928 −3.093 21.725 −0.983 −2.103 21.725 −0.993 −3.251 21.725 −1.014 −3.303 21.725 −1.026 −2.141 21.725 −1.036 −3.356 21.725 −1.058 −3.408 21.725 −1.069 −2.178 21.725 −1.080 −3.461 21.725 −1.102 −3.513 21.725 −1.112 −2.215 21.725 −1.125 −3.565 21.725 −1.148 −3.618 21.725 −1.155 −2.253 21.725 −1.171 −3.670 21.725 −1.194 −3.721 21.725 −1.198 −2.290 21.725 −1.218 −3.773 21.725 −1.240 −2.327 21.725 −1.243 −3.824 21.725 −1.268 −3.875 21.725 −1.283 −2.365 21.725 −1.294 −3.926 21.725 −1.321 −3.976 21.725 −1.326 −2.403 21.725 −1.350 −4.025 21.725 −1.368 −2.440 21.725 −1.379 −4.074 21.725 −1.410 −4.121 21.725 −1.411 −2.478 21.725 −1.443 −4.168 21.725 −1.453 −2.517 21.725 −1.478 −4.212 21.725 −1.494 −2.555 21.725 −1.516 −4.255 21.725 −1.536 −2.594 21.725 −1.556 −4.295 21.725 −1.577 −2.633 21.725 −1.600 −4.331 21.725 −1.618 −2.672 21.725 −1.647 −4.363 21.725 −1.659 −2.712 21.725 −1.697 −4.390 21.725 −1.700 −2.752 21.725 −1.740 −2.792 21.725 −1.750 −4.410 21.725 −1.780 −2.832 21.725 −1.806 −4.424 21.725 −1.899 −2.955 21.725 −1.919 −4.432 21.725 −1.938 −2.996 21.725 −1.976 −4.429 21.725 −1.977 −3.038 21.725 −2.015 −3.080 21.725 −2.032 −4.421 21.725 −2.054 −3.122 21.725 −2.088 −4.410 21.725 −2.092 −3.164 21.725 −2.130 −3.206 21.725 −2.143 −4.395 21.725 −2.168 −3.248 21.725 −2.197 −4.378 21.725 −2.206 −3.291 21.725 −2.243 −3.334 21.725 −2.250 −4.358 21.725 −2.280 −3.377 21.725 −2.303 −4.337 21.725 −2.317 −3.420 21.725 −2.354 −3.464 21.725 −2.354 −4.313 21.725 −2.390 −3.507 21.725 −2.404 −4.285 21.725 −2.426 −3.551 21.725 −2.450 −4.252 21.725 −2.450 −4.252 21.725 −2.463 −3.595 21.725 −2.491 −4.213 21.725 −2.498 −3.639 21.725 −2.525 −4.167 21.725 −2.532 −3.685 21.725 −2.552 −4.117 21.725 −2.562 −3.733 21.725 −2.574 −4.064 21.725 −2.585 −3.785 21.725 −2.589 −4.010 21.725 −2.599 −3.840 21.725 −2.599 −3.954 21.725 −2.603 −3.897 21.725 −0.559 −1.877 22.200 −0.568 −1.937 22.200 −0.579 −1.820 22.200 −0.584 −1.996 22.200 −0.599 −2.055 22.200 −0.615 −2.115 22.200 −0.624 −1.779 22.200 −0.678 −2.351 22.200 −0.682 −1.761 22.200 −0.694 −2.411 22.200 −0.710 −2.470 22.200 −0.726 −2.529 22.200 −0.742 −2.588 22.200 −0.742 −1.768 22.200 −0.758 −2.647 22.200 −0.775 −2.706 22.200 −0.791 −2.765 22.200 −0.794 −1.799 22.200 −0.808 −2.824 22.200 −0.825 −2.883 22.200 −0.831 −1.848 22.200 −0.842 −2.942 22.200 −0.859 −3.000 22.200 −0.865 −1.899 22.200 −0.877 −3.059 22.200 −0.895 −3.118 22.200 −0.900 −1.949 22.200 −0.913 −3.176 22.200 −0.931 −3.235 22.200 −0.936 −1.999 22.200 −0.950 −3.293 22.200 −0.969 −3.351 22.200 −0.971 −2.049 22.200 −0.989 −3.409 22.200 −1.007 −2.099 22.200 −1.009 −3.467 22.200 −1.030 −3.524 22.200 −1.043 −2.148 22.200 −1.051 −3.582 22.200 −1.073 −3.639 22.200 −1.080 −2.197 22.200 −1.096 −3.696 22.200 −1.117 −2.246 22.200 −1.119 −3.753 22.200 −1.143 −3.809 22.200 −1.155 −2.294 22.200 −1.168 −3.865 22.200 −1.192 −2.343 22.200 −1.195 −3.920 22.200 −1.222 −3.975 22.200 −1.230 −2.391 22.200 −1.251 −4.029 22.200 −1.269 −2.438 22.200 −1.281 −4.082 22.200 −1.346 −4.186 22.200 −1.382 −4.235 22.200 −1.386 −2.580 22.200 −1.420 −4.283 22.200 −1.425 −2.627 22.200 −1.461 −4.329 22.200 −1.465 −2.673 22.200 −1.505 −4.371 22.200 −1.506 −2.719 22.200 −1.546 −2.765 22.200 −1.553 −4.410 22.200 −1.587 −2.811 22.200 −1.603 −4.444 22.200 −1.629 −2.856 22.200 −1.658 −4.473 22.200 −1.670 −2.901 22.200 −1.712 −2.945 22.200 −1.715 −4.496 22.200 −1.754 −2.990 22.200 −1.774 −4.512 22.200 −1.796 −3.034 22.200 −1.834 −4.521 22.200 −1.839 −3.078 22.200 −1.882 −3.122 22.200 −1.895 −4.525 22.200 −1.925 −3.166 22.200 −1.956 −4.524 22.200 −1.968 −3.210 22.200 −2.011 −3.253 22.200 −2.017 −4.519 22.200 −2.054 −3.297 22.200 −2.078 −4.509 22.200 −2.097 −3.340 22.200 −2.138 −4.496 22.200 −2.140 −3.384 22.200 −2.183 −3.427 22.200 −2.197 −4.479 22.200 −2.226 −3.471 22.200 −2.254 −4.459 22.200 −2.269 −3.515 22.200 −2.311 −4.436 22.200 −2.311 −3.559 22.200 −2.354 −3.603 22.200 −2.366 −4.409 22.200 −2.396 −3.647 22.200 −2.419 −4.378 22.200 −2.438 −3.691 22.200 −2.509 −4.296 22.200 −2.520 −3.783 22.200 −2.542 −4.244 22.200 −2.554 −3.833 22.200 −2.567 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−1.076 −4.449 25.050 −1.081 −2.692 25.050 −1.105 −4.518 25.050 −1.113 −2.760 25.050 −1.136 −4.587 25.050 −1.146 −2.828 25.050 −1.169 −4.655 25.050 −1.179 −2.896 25.050 −1.203 −4.723 25.050 −1.213 −2.964 25.050 −1.239 −4.789 25.050 −1.247 −3.031 25.050 −1.278 −4.854 25.050 −1.282 −3.098 25.050 −1.318 −3.164 25.050 −1.319 −4.917 25.050 −1.355 −3.230 25.050 −1.363 −4.979 25.050 −1.393 −3.296 25.050 −1.409 −5.038 25.050 −1.431 −3.361 25.050 −1.459 −5.095 25.050 −1.471 −3.425 25.050 −1.512 −3.489 25.050 −1.512 −5.149 25.050 −1.554 −3.552 25.050 −1.569 −5.198 25.050 −1.597 −3.614 25.050 −1.630 −5.243 25.050 −1.641 −3.675 25.050 −1.687 −3.735 25.050 −1.695 −5.282 25.050 −1.734 −3.794 25.050 −1.763 −5.314 25.050 −1.885 −3.963 25.050 −1.910 −5.349 25.050 −1.939 −4.016 25.050 −1.985 −5.350 25.050 −1.995 −4.067 25.050 −2.052 −4.116 25.050 −2.060 −5.339 25.050 −2.112 −4.162 25.050 −2.132 −5.316 25.050 −2.173 −4.206 25.050 −2.200 −5.284 25.050 −2.237 −4.247 25.050 −2.264 −5.244 25.050 −2.302 −4.285 25.050 −2.324 −5.199 25.050 −2.369 −4.320 25.050 −2.380 −5.148 25.050 −2.432 −5.093 25.050 −2.434 −4.359 25.050 −2.481 −5.035 25.050 −2.492 −4.407 25.050 −2.525 −4.974 25.050 −2.536 −4.468 25.050 −2.561 −4.908 25.050 −2.561 −4.907 25.050 −2.567 −4.537 25.050 −2.586 −4.610 25.050 −2.586 −4.835 25.050 −2.596 −4.685 25.050 −2.596 −4.760 25.050 −0.343 −1.956 25.525 −0.353 −2.033 25.525 −0.366 −1.883 25.525 −0.366 −2.109 25.525 −0.380 −2.186 25.525 −0.394 −2.262 25.525 −0.408 −2.338 25.525 −0.421 −1.830 25.525 −0.422 −2.414 25.525 −0.436 −2.490 25.525 −0.450 −2.566 25.525 −0.465 −2.642 25.525 −0.479 −2.718 25.525 −0.494 −2.794 25.525 −0.495 −1.811 25.525 −0.509 −2.870 25.525 −0.524 −2.946 25.525 −0.571 −3.174 25.525 −0.588 −3.250 25.525 −0.604 −3.325 25.525 −0.618 −1.892 25.525 −0.621 −3.401 25.525 −0.638 −3.476 25.525 −0.652 −1.962 25.525 −0.656 −3.552 25.525 −0.674 −3.627 25.525 −0.685 −2.032 25.525 −0.692 −3.702 25.525 −0.711 −3.777 25.525 −0.717 −2.102 25.525 −0.731 −3.852 25.525 −0.750 −2.172 25.525 −0.751 −3.927 25.525 −0.771 −4.002 25.525 −0.782 −2.243 25.525 −0.793 −4.076 25.525 −0.815 −2.313 25.525 −0.815 −4.150 25.525 −0.838 −4.224 25.525 −0.847 −2.384 25.525 −0.861 −4.298 25.525 −0.879 −2.454 25.525 −0.886 −4.372 25.525 −0.911 −2.525 25.525 −0.912 −4.444 25.525 −0.939 −4.517 25.525 −0.943 −2.595 25.525 −0.968 −4.589 25.525 −0.975 −2.666 25.525 −0.998 −4.660 25.525 −1.006 −2.736 25.525 −1.030 −4.731 25.525 −1.038 −2.807 25.525 −1.063 −4.801 25.525 −1.070 −2.878 25.525 −1.099 −4.869 25.525 −1.102 −2.948 25.525 −1.135 −3.018 25.525 −1.138 −4.936 25.525 −1.167 −3.089 25.525 −1.179 −5.002 25.525 −1.200 −3.159 25.525 −1.223 −5.066 25.525 −1.234 −3.229 25.525 −1.322 −5.185 25.525 −1.337 −3.437 25.525 −1.373 −3.505 25.525 −1.377 −5.239 25.525 −1.409 −3.574 25.525 −1.437 −5.289 25.525 −1.447 −3.642 25.525 −1.485 −3.709 25.525 −1.500 −5.333 25.525 −1.524 −3.775 25.525 −1.565 −3.841 25.525 −1.568 −5.371 25.525 −1.608 −3.906 25.525 −1.638 −5.403 25.525 −1.652 −3.970 25.525 −1.697 −4.032 25.525 −1.711 −5.429 25.525 −1.745 −4.093 25.525 −1.785 −5.450 25.525 −1.795 −4.152 25.525 −1.847 −4.210 25.525 −1.861 −5.466 25.525 −1.902 −4.264 25.525 −1.938 −5.479 25.525 −1.959 −4.316 25.525 −2.015 −5.486 25.525 −2.019 −4.366 25.525 −2.082 −4.411 25.525 −2.092 −5.487 25.525 −2.147 −4.454 25.525 −2.169 −5.479 25.525 −2.213 −4.493 25.525 −2.213 −4.493 25.525 −2.245 −5.463 25.525 −2.283 −4.527 25.525 −2.318 −5.437 25.525 −2.353 −4.560 25.525 −2.386 −5.400 25.525 −2.420 −4.599 25.525 −2.446 −5.352 25.525 −2.479 −4.648 25.525 −2.498 −5.294 25.525 −2.525 −4.710 25.525 −2.539 −5.229 25.525 −2.559 −4.780 25.525 −2.572 −5.159 25.525 −2.581 −4.854 25.525

It will also be appreciated that the internal core profile of the nozzle airfoil disclosed in the above table may be scaled up or down geometrically for use in other similar turbine designs. Consequently, the coordinate values set forth in Table I may be scaled upwardly or downwardly such that the internal profile shape of the nozzle airfoil remains unchanged. A scaled version of the coordinates of Table I would be represented by X, Y and Z coordinate values of Table I multiplied or divided by a constant number.

While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims. 

1. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.
 2. A turbine nozzle segment according to claim 1 forming part of a first stage of a turbine.
 3. A turbine nozzle segment according to claim 1 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.
 4. A turbine nozzle segment according to claim 1 wherein the X, Y and Z distances are scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile.
 5. A turbine comprising a plurality of nozzle segments arranged in a circumferential array about an axis of the turbine, each said nozzle segment including inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.
 6. A turbine according to claim 5 forming part of a first stage of a turbine.
 7. A turbine according to claim 5 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.
 8. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.
 9. A turbine nozzle segment according to claim 8 forming part of a first stage of a turbine.
 10. A turbine nozzle segment according to claim 8 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.
 11. A turbine comprising a plurality of nozzle segments in a circumferential array about an axis of the turbine, each said segment having inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from said turbine axis to planes extending normal to the radii, and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.
 12. A turbine according to claim 11 forming part of a first stage of a turbine.
 13. A turbine according to claim 11 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location. 